Single-concave-cavity trapped vortex combustion chamber with light-transmitting swirler

Abstract

The invention relates to the technical field of gas turbines, in particular to a single-concave-cavity trapped vortex combustion chamber with a light-transmitting cyclone. According to the single-concave-cavity trapped vortex combustion chamber with the main combustion stage air inlet structure being the light-transmitting cyclone, the design defects in an existing trapped vortex combustion chamber scheme are overcome, and by strengthening mainstream oil and gas mixing, the flame tube wall temperature and the temperature gradient are further reduced, and the temperature field quality of an outlet of the combustion chamber is improved. According to the main combustion stage air inlet structure, the light-transmitting swirler and the bluff bodies are combined, most main combustion stage air enters the combustion area through the light-transmitting swirler, and only a small part of main combustion stage air enters the combustion area through the gap between the bluff bodies located on the upper side and the lower side of the light-transmitting swirler. The total pressure loss of the combustion chamber and mixing of mainstream oil and gas are comprehensively considered, the hydrocyclone with light transmission can be matched with a simple centrifugal nozzle, an oil supply system is simple, the quality of a temperature field at an outlet of the combustion chamber is improved, and the wall temperature and the temperature gradient of a flame tube are further reduced.

Description

Technical Field

[0001] The present disclosure relates to the technical field of gas turbines, and particularly to a single recessed cavity vortex combustion chamber with a light-transmitting swirler. Background Art

[0002] Based on the development requirements of high-performance aero power plants, the inlet temperature and temperature rise of the combustion chamber are further increased, but the requirements for the performance of the combustion chamber are not reduced. On the contrary, some performance indicators of the combustion chamber even increase. For example, the combustion chamber needs to operate stably within a wider fuel-air range, the quality of the temperature field at the outlet of the combustion chamber is further improved, and the life of the flame tube is maintained or even increased on the premise of reducing the quantity and quality of the cooling air.

[0003] Regarding the many technical challenges in the research and development of high-temperature-rise combustion chambers, on the one hand, it can be solved by adopting fuel staging and combustion zoning on a conventional swirler combustion chamber. On the other hand, it can be solved by exploring a new combustion organization method and developing a new concept combustion chamber. The vortex combustion chamber is a new concept combustion chamber. From its principle and structure, the vortex combustion chamber "naturally" belongs to the category of staged fuel supply and zoned combustion.

[0004] In the vortex combustion chamber, the vortex region serves as the duty class. By reasonably organizing the flow field in the vortex region and matching the fuel-air in the vortex region, a vortex and fuel-air distribution that is not easily affected by the main flow is formed in the vortex region, so that the vortex region can operate stably under various working conditions. The main combustion stage air enters the combustion zone through a combined structure of a splitter bluff body and a radial flame tube. Since the tangential flow of the main combustion stage air is weak, the uniformity of the fuel-air in the space of the main combustion stage is worse than that of the conventional swirler. Therefore, in the existing main combustion stage schemes of the vortex combustion chamber, most of the main combustion stage fuel adopts premixing, pre-evaporation or a combination of the two to strengthen the fuel-air mixing in the main combustion stage. However, this scheme will make the main combustion stage fuel supply structure and fuel system relatively complex, and on the other hand, the effect of fuel-air mixing in the main combustion stage is not very ideal. When the vortex combustion chamber is working, only the vortex region supplies fuel in small states, and the main combustion stage does not supply fuel; in large states, the vortex region and the main combustion stage supply fuel at the same time.

[0005] In summary, the wall temperature and temperature gradient of the flame tube of the existing vortex combustion chamber are relatively high, and the quality of the outlet temperature field is not ideal. From the perspective of engineering applications, there is still a long way to go for the existing vortex combustion chamber to be used as the main combustion chamber in aero engines. Summary of the Invention

[0006] In view of the above problems, the present disclosure provides a single recessed cavity vortex combustion chamber with a light-transmitting swirler.

[0007] In a first aspect, a single recessed cavity vortex combustion chamber with a light-transmitting swirler includes:

[0008] Inner casing;

[0009] Outer casing

[0010] The flame tube forms a single concave cavity structure. The inner casing, outer casing and flame tube form the inner and outer annulus ducts of the combustion chamber. The single concave cavity is located on the outer side as the pilot stage, and the main combustion stage is located on the inner side. The pilot stage and the main combustion stage are internally connected. The pilot stage forms a stationary double-vortex structure by relying on the intake of air through the front wall of the cavity and the intake of air through the rear wall of the cavity.

[0011] The main combustion stage air intake structure adopts a combination of a transparent swirler and a bluff body, which is used to supply air to the main combustion stage.

[0012] The combustion chamber ignition device is used for igniting the combustion chamber.

[0013] The fuel supply system is used to supply fuel to the main combustion stage and the pilot stage.

[0014] Furthermore, the main combustion stage air intake structure adopts a combination of a transparent swirler and a bluff body. Most of the main combustion stage air enters the combustion zone through the transparent swirler, and a small part of the main combustion stage air enters the combustion zone through the gaps between the bluff bodies located on the upper and lower sides of the transparent swirler.

[0015] Furthermore, the combustion chamber ignition device uses a high-energy ignition spark plug for direct ignition. The high-energy ignition spark plug is installed on the outer casing of the combustion chamber. The high-energy ignition spark plug extends from the outer casing of the combustion chamber to the bottom end face of the cavity and is flush with the bottom end face of the cavity.

[0016] Furthermore, the fuel supply system includes a main combustion stage fuel manifold and the main combustion stage fuel nozzles connected thereto, a pilot stage fuel manifold and the pilot stage fuel nozzles connected thereto.

[0017] Furthermore, the pilot stage fuel nozzles are arranged on the front wall of the cavity and are centrifugal nozzles that spray along the axial direction at a certain spray cone angle, and play the role of flame stabilization.

[0018] Using the cavity as the pilot stage to stabilize the flame makes a double-vortex structure that is not easily affected by the main flow formed in the cavity. At the same time, by matching the reasonable fuel supply through the pilot stage fuel nozzles, the cavity can maintain stable combustion under various working conditions.

[0019] Furthermore, the main combustion stage fuel nozzles adopt single-channel centrifugal nozzles or double-channel centrifugal nozzles, and are inserted into the transparent swirler along the center line of the transparent swirler. The outlet end face of the main combustion stage fuel nozzles is flush with the outlet end face of the hub of the transparent swirler.

[0020] Furthermore, inner and outer annular wall surfaces of the flame tube are provided with inner ring main combustion holes, outer ring mixing holes, inner ring mixing holes and cooling holes according to the needs of flow, mixing and cooling.

[0021] Furthermore, the cooling holes are multi-inclined holes with full divergence cooling.

[0022] Furthermore, the inner-ring main combustion holes are used to truncate the main flow recirculation zone, for afterburning, and to strengthen the main flow fuel-air mixing;

[0023] The outer-ring mixing holes and the inner-ring mixing holes are used to adjust the outlet temperature field.

[0024] In a second aspect, an engine

[0025] employs the above-described single cavity vortex-stabilized combustor with a light-transmissive swirler.

[0026] The present disclosure at least has the following beneficial effects:

[0027] The present disclosure provides a single cavity vortex-stabilized combustor with a light-transmissive swirler as the main combustion stage air inlet structure, overcoming the design deficiencies in existing vortex-stabilized combustor solutions. By strengthening the main flow fuel-air mixing, the wall temperature and temperature gradient of the flame tube are further reduced, and the quality of the combustor outlet temperature field is improved.

[0028] The main combustion stage air inlet structure of the present disclosure adopts a combination of a light-transmissive swirler and a bluff body. Most of the main combustion stage air enters the combustion zone through the light-transmissive swirler, and only a small part of the main combustion stage air enters the combustion zone through the gaps between the bluff bodies located on the upper and lower sides of the light-transmissive swirler.

[0029] The inner wall surface of the flame tube of the present disclosure is provided with main combustion holes, which are used to truncate the main flow recirculation zone, for afterburning, and to strengthen the fuel-air mixing in the main combustion stage.

[0030] The present disclosure comprehensively considers the total pressure loss of the combustor and the main flow fuel-air mixing. The light-transmissive swirler can be matched with a simple centrifugal nozzle, and the fuel supply system is relatively simple. The quality of the combustor outlet temperature field is improved, and the wall temperature and temperature gradient of the flame tube are further reduced.

[0031] Other features and advantages of the present disclosure will be described in the following description of the specification. And, some of them will become obvious from the description of the specification, or can be understood by implementing the present disclosure. The objectives and other advantages of the present disclosure can be achieved and obtained through the structures pointed out in the specification and the drawings. BRIEF DESCRIPTION OF THE DRAWINGS

[0032] In order to more clearly illustrate the technical solutions in the embodiments of the present disclosure or the prior art, the following will briefly introduce the drawings required for the description of the embodiments or the prior art. Obviously, the drawings in the following description are some embodiments of the present disclosure. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0033] Figure 1 It is a schematic diagram of the axial cross-section structure of the combustor in the embodiment of the present disclosure;

[0034] Figure 2 This is a schematic diagram of a cyclone structure with light transmission according to an embodiment of the present disclosure.

[0035] Description of the drawings: 101, outer casing of the combustion chamber; 102, duty fuel nozzle; 103, duty area; 104, high-energy ignition spark plug; 105, flame tube; 106, main combustion stage fuel nozzle; 107, cyclone with light transmission; 108, inner support plate; 109, outer support plate; The arrow represents the air flow direction. Specific embodiments

[0036] In order to make the objectives, technical solutions, and advantages of the embodiments of the present disclosure clearer, the technical solutions in the embodiments of the present disclosure will be clearly and completely described below with reference to the drawings in the embodiments of the present disclosure. Apparently, the described embodiments are some, but not all, of the embodiments of the present disclosure. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of the present disclosure without creative efforts shall fall within the protection scope of the present disclosure.

[0037] As Figure 1 shown, a single cavity vortex combustion chamber with a light-transmitting cyclone includes:

[0038] Inner casing;

[0039] Outer casing;

[0040] A flame tube that forms a single cavity structure. The inner casing, the outer casing, and the flame tube form the inner flow path and the outer flow path of the combustion chamber; The single cavity is located on the outside as the duty stage, and the main combustion stage is located on the inside. The duty stage and the main combustion stage are internally connected; The duty stage forms a stationary double vortex structure by the intake of air through the front wall and the rear wall of the cavity.

[0041] The main combustion stage air intake structure, which adopts a combination of a light-transmitting cyclone and a bluff body to supply air to the main combustion stage;

[0042] A combustion chamber ignition device for igniting the combustion chamber;

[0043] An oil supply system for supplying oil to the main combustion stage and the duty stage.

[0044] During specific implementation, the following is introduced:

[0045] Based on overcoming the deficiencies of existing vortex-stabilized combustors, the present disclosure proposes a single-recess vortex-stabilized combustor with a light-transmitting swirler as the main combustion stage intake structure. On the premise that the main flow does not affect the flow in the recess, the mixing of the main stream oil and gas is strengthened, so that the spatial distribution of the oil and gas has better uniformity, thereby further reducing the wall temperature and temperature gradient of the flame tube and improving the quality of the temperature field at the combustor outlet, providing a combustor solution for high-performance aeroengines. The basic principle of this combustor is to adopt the concept of staged and zoned combustion, which is divided into a pilot stage and a main combustion stage along the radial direction. A recess is used as the pilot stage to stabilize the flame. By reasonably organizing the air flow in the recess, a double-vortex structure that is not easily affected by the main flow is formed in the recess. At the same time, a reasonable fuel supply is matched, so that the recess can maintain stable combustion under various working conditions. Most of the air in the main combustion stage forms a weak swirl and enters the combustion zone through the light-transmitting swirler, and a small amount of air continues to enter the combustion zone in a straight-through state through the gaps between the bluff bodies. The setting of the bluff bodies can, on the one hand, ensure that the flow in the recess is not affected by the main flow, so that the recess maintains a wide range of flame stability performance, and on the other hand, it can also ensure that the flame in the recess spreads smoothly along the radial direction to the main stream, thereby igniting the main stream oil and gas. The main combustion stage intake structure adopts a light-transmitting swirler for three reasons. One is that it can strengthen the mixing of the main stream oil and gas, the second is that it will not cause large flow losses, and the third is that it can be matched with a simple centrifugal nozzle, so that the fuel supply system is relatively simple.

[0046] The specific solution is as follows: The combustor is a vortex-stabilized combustor with a single recess. The air entering the combustor is divided into three paths after passing through a diffuser and decelerator, and enters the flame tube through the inner ring, outer ring and head respectively. The combustor is radially staged, with the recess as the pilot stage located on the outside and the main combustion stage located on the inside. The pilot stage relies on the intake of air through the front wall and the rear wall of the recess to form a stationary double-vortex structure. At the same time, a centrifugal nozzle is matched to inject fuel axially, which can well perform the function of flame stabilization and can adapt to variable and complex working environments.

[0047] As Figure 2 shown, the main combustion stage intake structure adopts a combination of a light-transmitting swirler and bluff bodies. Most of the air in the main combustion stage enters the combustion zone through the light-transmitting swirler, and only a small part of the air in the main combustion stage enters the combustion zone through the gaps between the bluff bodies located on the upper and lower sides of the light-transmitting swirler. The design of the bluff bodies can, on the one hand, protect the flow in the recess from being affected by the swirling air in the main combustion stage, which is beneficial for the pilot stage to maintain good ignition and extinction performance and wide-range flame stability performance. On the other hand, the presence of the bluff bodies can strengthen the radial flow between the adjacent regions of the pilot stage and the main combustion stage, so that the flame in the recess can spread smoothly to the main combustion stage, thereby igniting the main combustion stage.

[0048] The combustion chamber is ignited directly by a high-energy ignition nozzle. The igniter is installed on the outer casing. The high-energy ignition nozzle extends from the outer casing to the bottom end face of the cavity and is flush with the bottom end face of the cavity. The fuel supply system includes the main combustion stage fuel main pipe, the duty class fuel main pipe, the main combustion stage fuel nozzle and the duty class fuel nozzle. The duty class fuel nozzle is set behind the front wall of the cavity and uses a centrifugal nozzle to spray along the axial direction at a certain spray cone angle to play the role of flame stabilization; the main combustion stage fuel nozzle is located inside the duty class fuel nozzle and uses a single oil circuit centrifugal nozzle or a double oil circuit centrifugal nozzle. It is inserted into the swirler along the center line of the swirler, and the nozzle outlet end face is flush with the swirler hub outlet end face. The inner and outer ring walls of the flame tube are arranged with inner ring main combustion holes, outer ring mixing holes, inner ring mixing holes and cooling holes according to the needs of flow, mixing and cooling. The flame tube cooling holes are fully divergent multi-inclined hole cooling, and the multi-inclined hole angle is a compound angle with a three-dimensional spatial angle; the inner ring main combustion holes are used to cut off the mainstream recirculation zone, supplementary combustion and enhance the mainstream oil and gas mixing, and the outer ring mixing holes and the inner ring mixing holes are used to adjust the outlet temperature field.

[0049] The present invention comprehensively considers the total pressure loss of the combustion chamber and the mixing of the mainstream oil and gas. The light-transmitting swirler can be matched with a simple centrifugal nozzle. The oil supply system is relatively simple, the quality of the temperature field at the combustion chamber outlet is improved, and the flame tube wall temperature and temperature gradient can be further reduced.

[0050] The present invention has undergone combustion chamber aerodynamic and structural design and three-dimensional performance numerical simulation. Judging from the combustion chamber performance of this scheme, the combustion chamber can maintain flame stability within a wide range of aerodynamic and thermal parameters and oil and gas parameters, the combustion chamber outlet temperature field quality is good, and the flame tube wall temperature and its temperature gradient are low, indicating that the combustion chamber scheme is feasible.

[0051] Although the present disclosure has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that they can still modify the technical solutions described in the aforementioned embodiments, or make equivalent replacements for some of the technical features therein; and these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present disclosure.

Claims

1. A single-cavity trapped vortex combustion chamber with a light-transmitting swirler, characterized in that: include: Inner receiver; Outer receiver; The flame tube forms a single concave cavity structure, and the inner casing, outer casing and flame tube form the inner duct and outer duct of the combustion chamber; the single concave cavity is located on the outside as the duty class, and the main combustion stage is located on the inside, and the duty class is connected to the inside of the main combustion stage; the duty class relies on the air intake of the front wall of the concave cavity and the air intake of the rear wall of the concave cavity to form a stationary double vortex structure; The main combustion stage air intake structure adopts a combination of a light-transmitting cyclone and a blunt body to supply air to the main combustion stage; A combustion chamber ignition device, used for ignition of the combustion chamber; The oil supply system is used to supply oil to the main fuel level and the duty level.

2. A single-cavity trapped vortex combustion chamber with a light-transmitting swirler according to claim 1, characterized in that: The main combustion stage air intake structure adopts a combination of a transparent cyclone and a blunt body, in which most of the main combustion stage air enters the combustion zone through the transparent cyclone, and a small part of the main combustion stage air enters the combustion zone through the gap between the blunt bodies on the upper and lower sides of the transparent cyclone.

3. A single-cavity trapped vortex combustion chamber with a light-transmitting swirler according to claim 1, characterized in that: The combustion chamber ignition device adopts a high-energy ignition nozzle for direct ignition. The high-energy ignition nozzle is installed on the combustion chamber outer casing. The high-energy ignition nozzle extends from the combustion chamber outer casing to the bottom end surface of the concave cavity and is flush with the bottom end surface of the concave cavity.

4. A single-cavity trapped vortex combustion chamber with a light-transmitting swirler according to claim 1, characterized in that: The fuel supply system includes a main fuel manifold and main fuel nozzles connected thereto, and a duty class fuel manifold and duty class fuel nozzles connected thereto.

5. A single-cavity trapped vortex combustion chamber with a light-transmitting swirler according to claim 4, characterized in that: The duty fuel nozzle is set on the front wall of the cavity, and uses a centrifugal nozzle to spray along the axial direction at a certain spray cone angle, which plays the role of flame stabilization; The concave cavity is used as the duty class to stabilize the flame, so that a double vortex structure that is not easily affected by the main flow is formed in the concave cavity. At the same time, reasonable fuel supply is matched through the duty class fuel nozzle, so that the concave cavity can maintain stable combustion under various working conditions.

6. A single-cavity trapped vortex combustion chamber with a light-transmitting swirler according to claim 4, characterized in that: The main combustion stage fuel nozzle adopts a single oil channel centrifugal nozzle or a double oil channel centrifugal nozzle, which is inserted into the light-transmitting cyclone along the center line of the light-transmitting cyclone. The outlet end face of the main combustion stage fuel nozzle is flush with the outlet end face of the light-transmitting cyclone hub.

7. A single-cavity trapped vortex combustion chamber with a light-transmitting swirler according to claim 1, characterized in that: The inner and outer ring walls of the flame tube are arranged with inner ring main combustion holes, outer ring mixing holes, inner ring mixing holes and cooling holes according to the needs of flow, mixing and cooling.

8. A single-cavity trapped vortex combustion chamber with a light-transmitting swirler according to claim 7, characterized in that: The cooling holes are fully divergent multi-inclined hole cooling.

9. The single-cavity trapped vortex combustion chamber with a light-transmitting swirler according to claim 7, characterized in that: The main combustion holes in the inner ring are used to cut off the mainstream recirculation area, supplementary combustion and strengthen the mainstream oil and gas mixing; The outer ring mixing holes and the inner ring mixing holes are used to adjust the outlet temperature field.

10. An engine, characterized in that: A single-cavity trapped vortex combustion chamber with a light-transmitting swirler as described in any one of claims 1 to 9 is adopted.

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